EP2995555A1 - Antriebssystem - Google Patents

Antriebssystem Download PDF

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Publication number
EP2995555A1
EP2995555A1 EP15183319.1A EP15183319A EP2995555A1 EP 2995555 A1 EP2995555 A1 EP 2995555A1 EP 15183319 A EP15183319 A EP 15183319A EP 2995555 A1 EP2995555 A1 EP 2995555A1
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EP
European Patent Office
Prior art keywords
energy
propulsor
storage system
energy storage
turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP15183319.1A
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English (en)
French (fr)
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EP2995555B1 (de
Inventor
Richard A. HIMMELMAN
Robert H. Perkinson
Stephen E. Tongue
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Hamilton Sundstrand Corp
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Hamilton Sundstrand Corp
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Publication of EP2995555A1 publication Critical patent/EP2995555A1/de
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/026—
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to the field of propulsion systems, and more specifically, cross-redundant hybrid electric pulsed power propulsion systems for aircraft.
  • a turbine In aircraft propulsion systems, a turbine often provides thrust, for example, via a propulsor such as a turbofan. However, a turbine becomes inefficient when operated at intermediate throttle settings. Moreover, often the aircraft has a separate auxiliary power unit and/or a generator to provide electrical power, but these additional systems increase the weight of the aircraft.
  • a method of operating a propulsion system may include propulsing a vehicle by a propulsor powered by an energy storage system, depleting energy stored in the energy storage system in response to the propulsing, pulsing on a turbine whereby energy may be provided to the energy storage system, replenishing, by the turbine, the energy stored in the energy storage system, and pulsing off the turbine in response to the replenishing.
  • the propulsion system may include a first propulsor, a first energy conversion system, a first energy storage system, and a first turbine.
  • the first propulsor may be in electrical communication with the first energy conversion system.
  • the first energy conversion system may receive an energy storage system electrical energy from the first energy storage system and may provide a conditioned energy storage system electrical energy to at least one of the first propulsor and an emergency system.
  • an aircraft may comprise a propulsion system.
  • the propulsion system may include a turbine engine.
  • turbine engines are inefficient when operated at intermediate throttle settings.
  • the turbine may be desired to operate at intermediate throttle settings, decreasing the efficiency of energy consumption. This raises the cost of operating the aircraft because the fuel is not utilized as efficiently at intermediate throttle settings as at a maximal or near maximal efficiency point, such as wide-open throttle or another designed maximal or near maximal efficiency point.
  • one manner of addressing these inefficiencies includes implementing an energy storage system that can receive energy from the turbine and store it for later use.
  • the turbine may be shut down, and the energy storage system may provide stored energy to a propulsor, so that the aircraft can be propelled without a need for the turbine to be running.
  • the turbine may be said to be pulsed.
  • stored energy may be used to propel the aircraft instead.
  • aircraft may include multiple propulsors.
  • a twin-engine aircraft may have a turbine for each wing.
  • the energy storage system can be connected in such a manner that it may store energy from either turbine.
  • further efficiency gains may be realized by only operating a single turbine to charge the energy storage system.
  • the need for an aircraft auxiliary power unit may be eliminated by drawing aircraft electrical power from the energy storage system.
  • the need for an emergency ram air turbine may be eliminated.
  • the turbine and/or propulsors may be permitted to windmill in response to passing air.
  • the kinetic energy of the windmilling turbine and/or propulsors may be stored in an energy storage system, where it may be drawn by emergency systems, such as emergency hydraulic systems, or by engine re-starter systems, or emergency electrical systems, such as emergency communications systems, or by any other suitable aircraft system.
  • emergency systems such as emergency hydraulic systems, or by engine re-starter systems
  • emergency electrical systems such as emergency communications systems, or by any other suitable aircraft system.
  • the aircraft when the aircraft is on the ground, it may be plugged into the airport electrical grid to recharge the energy storage system.
  • energy may be flowed from the energy storage system to the other aircraft systems, such as electrical systems, avionics systems and/or the aircraft propulsors.
  • the turbines may be left off during ground operations.
  • the turbines may be started for takeoff and climb, and may be utilized to also recharge the energy storage system.
  • the turbines may be turned off and the energy storage system may provide energy for the propulsors.
  • One or more turbines may be restarted as needed to recharge the energy storage system.
  • the aircraft auxiliary power unit may be eliminated and the electrical power for other aircraft systems can provided by the energy storage system.
  • one or multiple propulsions systems may be implemented and may be interconnected.
  • the system may store energy and may release energy, permitting the turbine to avoid operation in inefficient ranges, as well as eliminating heavy and/or costly auxiliary power units and/or emergency ram air turbines.
  • a propulsion system 10 may comprise a propulsor 2, an energy conversion system 4, a turbine 6, and an energy storage system 8.
  • the propulsion system may further comprise an emergency system 9.
  • the propulsion system may accept energy from the turbine 6 and convert it via energy conversion system 4 to a form suited to drive the propulsor 2 and/or for storage in the energy storage system 8.
  • the propulsor 2 comprises a kinetic energy imparting apparatus.
  • the propulsor may comprise a propeller system driven by an electrical motor.
  • the propulsor may also comprise a gear reduction apparatus disposed between the propeller system and the electrical motor, whereby the electrical motor drives the propeller system.
  • the propulsor may receive electrical energy from an energy conversion system 4 and may utilize it to turn an electrical motor, thus turning a propeller.
  • the propulsor may comprise a propeller, or may comprise a ducted fan, or may comprise any mechanism by which thrust may be imparted to an airframe.
  • the propulsor may provide a further mechanism for the sourcing of energy, such as to eliminate the need for an emergency ram air turbine, or otherwise to provide energy to the energy conversion system.
  • the propulsor may be permitted to windmill in response to passing air.
  • the kinetic energy of the windmilling propulsor may be stored in an energy storage system, where it may be drawn by emergency system 9, such as emergency hydraulic systems, or by engine re-starter systems, or emergency electrical systems, such as emergency communications systems, or by any other suitable aircraft system.
  • the energy conversion system 4 comprises a mechanical to electrical energy converting apparatus.
  • the energy conversion system 4 may receive mechanical energy from a turbine 6 via a rotating shaft and may convert this energy into electricity, such as by a generator.
  • the energy conversion system 4 directs this electrical energy to a propulsor 2, or to an energy storage system 8, or to both a propulsor 2 and to an energy storage system 8.
  • the energy conversion system 4 may receive electrical energy from an energy storage system 8 and convey it to a propulsor 2.
  • the energy conversion system 4 may also pass through electrical energy from an energy storage system 8 to a propulsor 2, although it may also convert electrical energy among different voltages, waveforms, currents, phases, or other forms.
  • the energy conversion system 4 may further receive electrical energy from an energy storage system 8 and convey it to a turbine 6.
  • the energy conversion system 4 may receive electrical energy from the energy storage system 8, convert it to mechanical energy, such as by a motor (e.g., a generator run in reverse), and deliver it to the turbine 6 via a rotating shaft, such as for restarting the turbine.
  • a motor e.g., a generator run in reverse
  • the energy storage system 8 comprises an electrical energy storing apparatus.
  • the energy storage system 8 may comprise one or more batteries.
  • the energy storage system 8 may receive electrical energy from an energy conversion system 4 and may store it.
  • the energy storage system 8 may deliver electrical energy to an energy conversion system 4, for ultimate delivery to a propulsor 2, or for conversion to mechanical energy and delivery to a turbine 6, such as for restarting the turbine 6.
  • an interconnected propulsion system 20 may comprise a first propulsion system 10-1 and a second propulsion system 10-2.
  • the first propulsion system 10-1 may comprise a first energy conversion system 4-1, a first turbine 6-1, a first energy storage system 8-1 and a first propulsor 2-1 interconnected as discussed herein.
  • the second propulsion system 10-2 may comprise a second energy conversion system 4-2, a second turbine 6-2, a second energy storage system 8-2, and a second propulsor 2-2 interconnected as discussed herein.
  • An interconnected propulsion system 20 may further comprise an interconnection element 22.
  • An interconnection element 22 may comprise electrical wiring disposed between the first propulsor 2-1 and the second propulsor 2-2. In this manner, the propulsors may be connected in parallel. Accordingly, either propulsor, and/or both propulsors may receive electrical energy from either energy conversion system, and/or both energy conversion systems. Similarly, either propulsor and/or both propulsors may deliver energy to either energy conversion system and/or both conversion systems.
  • the interconnection element 22 comprises an interconnection disposed between the first propulsor 2-1 and first energy conversion system 4-1 and connecting between the second propulsor 2-2 and the second energy conversion system 4-2. However, in further embodiments, the interconnection element 22 may be disposed between the energy conversion system and energy storage system, or any other interconnection point in the systems.
  • a dual-propulsor propulsion system 30 may comprise a first turbine 6-1, a first energy conversion system 4-1, and a first energy storage system 8-1, arranged as discussed herein.
  • a first propulsor 2-1 may be interconnected with the first energy conversion system 4-1, and an interconnection element 22 disposed between the first propulsor 2-1 and the energy conversion system 4-1, whereby the second propulsor 2-2 is also connected to the same first energy conversion system 4-1.
  • a turbine 6 may comprise gas turbine. However, turbine 6 may comprise various supporting systems, such as pumps, gearboxes, valves, and tubing. In various embodiments, the turbine 6 comprises a turbofan engine. In further embodiments, the turbine 6 comprises a turboprop engine, or a turbojet engine, or any other form of turbine engine. In various embodiments, the turbine 6 does not comprise a turbine engine, but comprises a fuel cell. Moreover, in still further embodiments, the turbine 6 does not comprise a turbine engine, but comprises an internal combustion engine, for example, an internal combustion engine having pistons, and/or an internal combustion engine comprising a rotary engine.
  • the turbine 6 may comprise an internal combustion reciprocating engine, such as one based on Otto cycle, or Diesel cycle, or Miller cycle, or Atkinson cycle, or an internal combustion rotary engine (e.g., Wankel), or another internal combustion engine, or an external combustion continuous engine such as a gas turbine engine (based on the open Brayton cycle), or any other engine.
  • the turbine 6 can be an internal combustion engine which is aspirated naturally or with forced induction (e.g., turbocharged or super-charged).
  • the turbine 6 may have a turbocharger which may be a single or dual (twin) configuration using a centrifugal compressor directly coupled to either an axial inflow or centrifugal inflow turbine, and whose operation may be further enhanced by structures such as: variable vane geometries, articulated waste gates, blow-off/pressure relief valves, and by methods such as: intercooling, water spray injection, etc.
  • An energy conversion system 4 may comprise a rectifier/inverter 34.
  • a rectifier/inverter 34 may comprise an electrical circuit comprising diodes and/or controllers and/or transistors and/or other electrical components whereby alternating-current electricity, such as that provided by a high-speed electric machine 35 (discussed below) is converted into direct-current electricity (e.g., "rectified").
  • a rectifier/inverter 34 may comprise an electrical circuit comprising diodes and/or controllers and/or transistors and/or other electrical components whereby direct-current electricity, such as that provided by an energy storage system 8 (discussed below) may be converted into alternating-current electricity, such as to drive a high speed electric machine 35 as an electric motor.
  • the rectifier/inverter 34 conditions electrical energy received from a high-speed electric machine (high speed electric machine electrical energy), conditions electrical energy received from an energy storage system (energy storage system electrical energy), and/or conditions electrical energy received from other sources, such as a windmilling propulsor.
  • an energy conversion system 4 may comprise a high-speed electric machine 35.
  • a high-speed electric machine 35 may comprise an electric motor and/or a generator depending on how it is implemented.
  • a high speed electric machine 35 may operate as a motor in response to electrical current, for example an alternating current being provided, such as by a rectifier/inverter 34.
  • the high-speed electric machine 35 may rotate a shaft, which may be mechanically connected to a turbine 6 and which may spin the turbine compressor such as when the turbine is being started.
  • a high-speed electric machine 35 may operate as a generator in response a rotating shaft being spun, such as by a turbine 6.
  • the high-speed electric machine 35 may produce an alternating current that is provided to the rectifier/inverter 34, for rectification into a direct current and utilization by other system(s).
  • An energy storage system 8 may comprise a battery 36.
  • Battery 36 may comprise a lithium-ion battery, a lithium-ion polymer battery, a lead acid battery, a nickel metal hydride battery, a nickel cadmium battery, a fuel cell, ultra-capacitors, super-capacitors or any other apparatus whereby electrical energy may be stored, for example, a combination of one or more ultra-capacitor and/or super-capacitor and one or more battery.
  • An energy storage system 8 may further comprise a DC/DC converter/battery charger 37.
  • the DC/DC converter/battery charger 37 may receive electrical energy, such as from a propulsor 2 and/or an energy conversion system 4 and may convert it to a form suitable for storage in the battery 36.
  • the DC/DC converter/battery charger 37 may convert a direct current having a first current and first voltage to a direct current having a second current and second voltage more suitable for storage in the battery 36.
  • the DC/DC converter/battery charger may convert an alternating current to a direct current suitable for storage in the battery.
  • the DC/DC converter/battery charger 37 may convert a direct current having a first current and a first voltage as provided by the battery into a direct current having a second current and a second voltage or into an alternating current, for example, for provision to an energy conversion system 4 and/or a propulsor 2.
  • the electrical energy may be transformed to any form suitable for storage in the battery 36 and for utilization by other aircraft systems when drawn from the battery 36.
  • a propulsor 2 may further comprise various embodiments.
  • a propulsor 2 may comprise different configurations.
  • a propulsor 2 may comprise a motor drive 33, a motor 32, and a propeller 31.
  • the motor drive 33 may receive electrical energy, and provide power and control signals to a motor 32 whereby the motor 32 may be directed to spin a propeller 31 in response.
  • the motor drive 33 may comprise a three-phase solid-state motor controller.
  • the motor drive 33 may receive electrical energy and provide three-phase alternating current power to the motor, in order to control the speed and direction of the motor.
  • the motor drive 33 may comprise a five-phase solid-state motor controller, such as to drive a switched reluctance motor, or may comprise a six-phase solid-state motor controller, or any number 'n' phase motor controller.
  • the motor drive 33 provides pulse-width modulated power to the motor; however, in further embodiments, the motor drive 33 provides current limited power to the motor.
  • the motor drive 33 may comprise any architecture suitable for implementation with a desired motor 32.
  • the motor 32 may comprise brushless motor, such as a three-phase brushless motor, or a five-phase brushless motor, or a six-phase brushless motor, or any number 'n' phase motor.
  • the motor 32 may comprise a brushed motor.
  • the motor 32 may comprise a switched reluctance motor.
  • the motor 32 may comprise supporting hardware such as gearboxes, mechanical linkages, shafts, flywheels, etc.
  • the propeller 31 may comprise a propeller in mechanical connection to the motor 32.
  • the propeller 31 may comprise a constant speed propeller, or a turbofan, or a constant pitch propeller, or a ducted fan, or any other mechanism by which an aircraft may be propulsed.
  • the propeller 31 may comprise additional controllers and/or circuitry, for example, to control propeller pitch and/or speed.
  • the propeller 31 comprises two blades, or three blades, or four blades, or five blades, or six blades, or any number of blades and/or vanes, for example, in the event that the propeller comprises a ducted fan.
  • the propeller may comprise a housing and/or shroud, or any apparatus whereby airflow may be directed through the blades of the propeller.
  • a propulsor 2 comprises a single propeller 31, a single motor 32, and a single motor drive 33, as illustrated in FIG. 5B .
  • a propulsor 2 may comprise multiple propellers.
  • a propulsor 2 may comprise a propeller 31 driven by a motor 32 which is controlled by a motor drive 33.
  • the propulsor 2 may further comprise a second propeller 41, driven by a second motor 42, which is controlled by a second motor drive 43.
  • a propulsor 2 may comprise two propellers (31, 41) which are counterrotating.
  • a first propulsion system 10-1 may comprise a first turbine 6-1, a first energy conversion system 4-1, a first energy storage system 8-1, and a first propulsor 2-1.
  • a second propulsion system 10-2 may comprise a second turbine 6-2, a second energy conversion system 4-2, a second energy storage system 8-2, and a second propulsor 2-2.
  • the first propulsion system 10-1 and second propulsion system 10-2 may be interconnected by an interconnection element 22 disposed as illustrated, between the first propulsor 2-1 and first energy conversion system 4-1 and interconnecting between the second propulsor 2-2 and second energy conversion system 4-2.
  • the first energy conversion system 4-1 may comprise a first energy conversion system high-speed electric machine 35-1 and a first energy conversion system rectifier/inverter 34-1.
  • the second energy conversion system 4-2 may comprise a second energy conversion system high-speed electric machine 35-2 and a second energy conversion system rectifier/inverter 34-2.
  • the first energy storage system 8-1 may comprise a first energy storage system battery 36-1 and a first energy storage system DC/DC converter/battery charger 37-1.
  • the second energy storage system 8-2 may comprise a second energy storage system battery 36-2 and a second energy storage system DC/DC converter/battery charger 37-2.
  • the first propulsor 2-1 may comprise a first propulsor propeller 31-1, a first propulsor motor 32-1 and a first propulsor motor drive 33-1.
  • the second propulsor 2-2 may comprise a second propulsor propeller 31-2, a second propulsor motor 32-2 and a second propulsor motor drive 33-2.
  • the first propulsor 2-1 and/or second propulsor 2-2 may be configured according to FIG. 5B , as discussed herein.
  • an interconnected propulsion system 20 may comprise a first propulsion system 10-1 having a propulsor according to FIG. 5A , and a second propulsion system 10-2 having a propulsor according to FIG. 5B , or also according to FIG. 5A , or comprising any other combination and/or arrangement of elements.
  • a propulsion system may operate according to different methods.
  • a method 700 may include pulsing off a turbine (Step 701). This may comprise shutting the turbine down, or may comprise retarding the turbine throttle setting to an idle setting, for example, a flight idle or a ground idle.
  • the method may further include propulsing the aircraft by a propulsor powered by an energy storage system (Step 703).
  • the energy stored within the energy storage system may be depleted (Step 705).
  • the method may include pulsing on the turbine (Step 707). This may include advancing the turbine throttle setting to an optimal efficiency setting.
  • the energy storage system may be recharged (Step 709).
  • the method 700 may then return to step 701 and the turbine may be pulsed off. In this manner, the duty cycle of the turbine is decreased such that the turbine spends less time operating at non-optimal throttle settings.
  • a propulsion system may be made of many different materials or combinations of materials.
  • various components of the system may be made from metal.
  • various aspects of an propulsion system may comprise metal, such as titanium, aluminum, steel, or stainless steel, though it may alternatively comprise numerous other materials configured to provide support, such as, for example, composite, ceramic, plastics, polymers, alloys, glass, binder, epoxy, polyester, acrylic, or any material or combination of materials having desired material properties, such as heat tolerance, strength, stiffness, or weight.
  • various portions of a propulsion system as disclosed herein are made of different materials or combinations of materials, and/or may comprise coatings.
  • a propulsion system may comprise multiple materials, or any material configuration suitable to enhance or reinforce the resiliency and/or support of the system when subjected to wear in an aircraft operating environment or to satisfy other desired electromagnetic, chemical, physical, or material properties, for example radar signature, heat generation, efficiency, electrical output, strength, or heat tolerance.
  • various components may comprise an austenitic nickel-chromium-based alloy such as Inconel®, which is available from Special Metals Corporation of New Hartford, New York, USA.
  • various components may comprise ceramic matrix composite (CMC).
  • CMC ceramic matrix composite
  • various aspects may comprise refractory metal, for example, an alloy of titanium, for example titanium-zirconium-molybdenum (TZM).
  • hydraulic fluid may comprise any hydraulic oil or fluid.
  • fuel may be a kerosene-type jet fuel such as Jet A, Jet A-1, JP-5, and/or JP-8.
  • fuel may be a wide-cut or naphtha-type jet fuel, such as Jet B and/or JP4.
  • fuel may be a synthetic fuel, such as Fischer-Tropsch Synthetic Paraffinic Kerosene (FT-SPK) fuel, or Bio-Derived Synthetic Paraffinic Kerosene (Bio-SPK), or may be any other suitable fuel, for example, gasoline or diesel.
  • FT-SPK Fischer-Tropsch Synthetic Paraffinic Kerosene
  • Bio-SPK Bio-Derived Synthetic Paraffinic Kerosene
  • references to "various embodiments”, “one embodiment”, “an embodiment”, “an example embodiment”, etc. indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments.
EP15183319.1A 2014-09-02 2015-09-01 Antriebssystem Active EP2995555B1 (de)

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US14/475,146 US20160257416A1 (en) 2014-09-02 2014-09-02 Propulsion system

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EP2995555A1 true EP2995555A1 (de) 2016-03-16
EP2995555B1 EP2995555B1 (de) 2019-02-06

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Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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EP3403932A1 (de) * 2017-05-17 2018-11-21 General Electric Company Antriebssystem für ein flugzeug
EP3415436A1 (de) * 2017-06-12 2018-12-19 General Electric Company Antriebssystem für ein flugzeug
EP3584168A1 (de) * 2018-06-20 2019-12-25 Airbus Operations, S.L.U. Turbomaschine für ein flugzeug
FR3085667A1 (fr) * 2018-09-12 2020-03-13 Safran Ensemble propulsif hybride serie pour aeronef
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EP3931094A4 (de) * 2019-03-01 2022-11-16 United Technologies Advanced Projects, Inc. Elektrisches antriebssystem für flugzeug mit einem hybriden elektrischen antriebssystem
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Families Citing this family (26)

* Cited by examiner, † Cited by third party
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US9764837B2 (en) * 2014-11-14 2017-09-19 Top Flight Technologies, Inc. Micro hybrid generator system drone
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US10000293B2 (en) 2015-01-23 2018-06-19 General Electric Company Gas-electric propulsion system for an aircraft
US20160304214A1 (en) * 2015-04-20 2016-10-20 Hamilton Sundstrand Corporation Emergency power sources for propulsion systems
US10814991B2 (en) * 2015-11-09 2020-10-27 General Electric Company Propulsion system and methods of use thereof
US10450886B2 (en) * 2015-12-22 2019-10-22 General Electric Company Hybrid propulsion system including a chemically rechargeable ultra-capacitor
US9764848B1 (en) * 2016-03-07 2017-09-19 General Electric Company Propulsion system for an aircraft
US10604266B2 (en) * 2016-05-16 2020-03-31 Rolls-Royce Corporation Electrical assist for aircraft
US10017266B2 (en) * 2016-09-22 2018-07-10 Top Flight Technologies, Inc. Power generation and distribution for vehicle propulsion
JP2019534665A (ja) * 2016-10-20 2019-11-28 トップ フライト テクノロジーズ， インコーポレイテッド ハイブリッド電力システム特性評価
US10647438B2 (en) 2016-12-07 2020-05-12 Rolls-Royce North American Technologies, Inc. Variable pitch for coordinated control
DE102016224779B4 (de) * 2016-12-13 2019-08-29 Airbus Defence and Space GmbH Elektrische Antriebsanordnung für ein Luftfahrzeug, Verfahren zu deren Betrieb sowie Luftfahrzeug
US10934008B2 (en) * 2017-02-10 2021-03-02 General Electric Company Dual function aircraft
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US20180265213A1 (en) * 2017-03-17 2018-09-20 Hamilton Sundstrand Corporation Emergency power generation via electrically driven tail cone boundary layer ingestion thruster
US10689082B2 (en) * 2017-04-12 2020-06-23 Rolls-Royce North American Technologies, Inc. Mechanically and electrically distributed propulsion
US10633104B2 (en) * 2017-05-17 2020-04-28 General Electric Company Hybrid-electric propulsion system for an aircraft
US10800536B2 (en) * 2017-06-09 2020-10-13 General Electric Company Propulsion system for an aircraft
US10718598B2 (en) 2017-06-23 2020-07-21 Hamilton Sundstrand Corporation Series hybrid architecture for an unmanned underwater vehicle propulsion system
US10822100B2 (en) 2017-06-26 2020-11-03 General Electric Company Hybrid electric propulsion system for an aircraft
US11097849B2 (en) 2018-09-10 2021-08-24 General Electric Company Aircraft having an aft engine
US11370554B2 (en) 2018-11-08 2022-06-28 Rolls-Royce North American Technologies, Inc. Hybrid propulsion systems
US11465518B2 (en) 2020-04-17 2022-10-11 Hamilton Sundstrand Corporation Charging scheme for electric propulsion systems
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GB202205347D0 (en) * 2022-04-12 2022-05-25 Rolls Royce Plc Propulsion system
US20240060452A1 (en) * 2022-08-22 2024-02-22 General Electric Company Propulsion system including an electric machine for starting a gas turbine engine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1851857A (en) * 1931-04-04 1932-03-29 Marney Arthur Aeroplane
WO2009050456A2 (en) * 2007-10-15 2009-04-23 Langford Performance Engineering Limited A hybrid powertrain
US20090145998A1 (en) * 2008-01-11 2009-06-11 Salyer Ival O Aircraft using turbo-electric hybrid propulsion system
US20110147105A1 (en) * 2008-08-21 2011-06-23 Emil Dimitrov Hybrid drive device for motor vehicles
DE102010021022A1 (de) * 2010-05-19 2011-11-24 Eads Deutschland Gmbh Kippflügel-Flugzeug
DE102010021026A1 (de) * 2010-05-19 2011-11-24 Eads Deutschland Gmbh Hybrides Antriebs- und Energiesystem für Fluggeräte
US20140203760A1 (en) * 2013-01-18 2014-07-24 Caterpillar Inc. Turbine engine hybrid power supply

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4199037A (en) * 1978-05-19 1980-04-22 White Bruce D Electric automobile
US20120209456A1 (en) * 2011-02-15 2012-08-16 Government Of The United States, As Represented By The Secretary Of The Air Force Parallel Hybrid-Electric Propulsion Systems for Unmanned Aircraft
DE102011105880B4 (de) * 2011-06-14 2014-05-08 Eads Deutschland Gmbh Elektrische Antriebsvorrrichtung für ein Luftfahrzeug
US20160176534A1 (en) * 2014-12-19 2016-06-23 Hamilton Sundstrand Corporation Emergency power sources for propulsion systems
US20160304214A1 (en) * 2015-04-20 2016-10-20 Hamilton Sundstrand Corporation Emergency power sources for propulsion systems

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1851857A (en) * 1931-04-04 1932-03-29 Marney Arthur Aeroplane
WO2009050456A2 (en) * 2007-10-15 2009-04-23 Langford Performance Engineering Limited A hybrid powertrain
US20090145998A1 (en) * 2008-01-11 2009-06-11 Salyer Ival O Aircraft using turbo-electric hybrid propulsion system
US20110147105A1 (en) * 2008-08-21 2011-06-23 Emil Dimitrov Hybrid drive device for motor vehicles
DE102010021022A1 (de) * 2010-05-19 2011-11-24 Eads Deutschland Gmbh Kippflügel-Flugzeug
DE102010021026A1 (de) * 2010-05-19 2011-11-24 Eads Deutschland Gmbh Hybrides Antriebs- und Energiesystem für Fluggeräte
US20140203760A1 (en) * 2013-01-18 2014-07-24 Caterpillar Inc. Turbine engine hybrid power supply

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2539756B (en) * 2015-05-13 2017-10-18 Rolls Royce Plc Aircraft propulsion system
GB2539756A (en) * 2015-05-13 2016-12-28 Rolls Royce Plc Aircraft propulsion system
EP3296212A1 (de) * 2016-09-19 2018-03-21 Rolls-Royce plc Flugzeugantriebssystem
US11542021B2 (en) 2016-09-19 2023-01-03 Rolls-Royce Plc Aircraft propulsion system
US10974836B2 (en) 2016-09-19 2021-04-13 Rolls-Royce Plc Aircraft propulsion system
US11827369B2 (en) 2017-04-21 2023-11-28 General Electric Company Propulsion system for an aircraft
EP3763623A1 (de) * 2017-04-21 2021-01-13 General Electric Company Antriebssystem für ein flugzeug
US10807729B2 (en) 2017-05-17 2020-10-20 General Electric Company Propulsion system for an aircraft
EP3403932A1 (de) * 2017-05-17 2018-11-21 General Electric Company Antriebssystem für ein flugzeug
EP4112475A1 (de) * 2017-05-17 2023-01-04 General Electric Company Antriebssystem für ein flugzeug
JP2019023068A (ja) * 2017-06-12 2019-02-14 ゼネラル・エレクトリック・カンパニイ 航空機用推進システム
US10676199B2 (en) 2017-06-12 2020-06-09 General Electric Company Propulsion system for an aircraft
US11427340B2 (en) 2017-06-12 2022-08-30 General Electric Company Propulsion system for an aircraft
EP4116197A1 (de) * 2017-06-12 2023-01-11 General Electric Company Antriebssystem für ein flugzeug
EP3415436A1 (de) * 2017-06-12 2018-12-19 General Electric Company Antriebssystem für ein flugzeug
EP3418674B1 (de) * 2017-06-23 2023-03-15 Hamilton Sundstrand Corporation Elektrisches antriebssystem eines unbemannten unterwasserfahrzeugs mit pulsierender leistung
EP3584168A1 (de) * 2018-06-20 2019-12-25 Airbus Operations, S.L.U. Turbomaschine für ein flugzeug
WO2020053502A3 (fr) * 2018-09-12 2020-06-04 Safran Ensemble propulsif hybride serie pour aeronef
FR3085667A1 (fr) * 2018-09-12 2020-03-13 Safran Ensemble propulsif hybride serie pour aeronef
EP3931094A4 (de) * 2019-03-01 2022-11-16 United Technologies Advanced Projects, Inc. Elektrisches antriebssystem für flugzeug mit einem hybriden elektrischen antriebssystem
EP3736526A1 (de) * 2019-05-10 2020-11-11 Hamilton Sundstrand Corporation Mehrfach benutzbarer anlasser für ein torpedoantriebssystem

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